EP2944764A1 - Bauteil, zugehöriges Gasturbinentriebwerk und Kühlverfahren - Google Patents

Bauteil, zugehöriges Gasturbinentriebwerk und Kühlverfahren Download PDF

Info

Publication number
EP2944764A1
EP2944764A1 EP15001485.0A EP15001485A EP2944764A1 EP 2944764 A1 EP2944764 A1 EP 2944764A1 EP 15001485 A EP15001485 A EP 15001485A EP 2944764 A1 EP2944764 A1 EP 2944764A1
Authority
EP
European Patent Office
Prior art keywords
heat transfer
tip
tip pocket
transfer augmentation
component
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP15001485.0A
Other languages
English (en)
French (fr)
Other versions
EP2944764B1 (de
EP2944764A8 (de
Inventor
designation of the inventor has not yet been filed The
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP2944764A1 publication Critical patent/EP2944764A1/de
Publication of EP2944764A8 publication Critical patent/EP2944764A8/de
Application granted granted Critical
Publication of EP2944764B1 publication Critical patent/EP2944764B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This disclosure relates to a gas turbine engine, and more particularly to a gas turbine engine component having an airfoil that includes a tip pocket.
  • the tip pocket may employ one or more heat transfer augmentation devices.
  • Gas turbine engines typically include a compressor section, a combustor section, and a turbine section. During operation, air is pressurized in the compressor section and is mixed with fuel and burned in the combustor section to generate hot combustion gases. The hot combustion gases are communicated through the turbine section, which extracts energy from the hot combustion gases to power the compressor section and other gas turbine engine loads.
  • cooling circuits that channel dedicated cooling fluids for cooling the component. It can be difficult to communicate enough cooling fluid to cool airfoil tips of the components. This may lead to airfoil tip burning.
  • a component according to an exemplary aspect of the present invention includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge.
  • the airfoil extends to a tip.
  • a tip pocket is formed in the tip and terminates prior to the trailing edge.
  • a heat transfer augmentation device is formed in the tip pocket.
  • the tip pocket includes a suction side lip, a pressure side lip, a leading edge lip and a trailing edge lip that extend radially outwardly from a floor.
  • the heat transfer augmentation device axially extends across at least one of the suction side lip and the pressure side lip.
  • the heat transfer augmentation device extends from the leading edge lip to the trailing edge lip.
  • the heat transfer augmentation device extends radially outwardly from the floor across at least one of the suction side lip and the pressure side lip.
  • the heat transfer augmentation device is slanted toward either the leading edge lip or the trailing edge lip.
  • the heat transfer augmentation device is formed on the floor and extends between the suction side lip and the pressure side lip.
  • the heat transfer augmentation device is tapered.
  • the heat transfer augmentation device is a chevron or a trip strip.
  • the heat transfer augmentation device is formed on a suction side lip of the tip pocket and a second heat transfer augmentation device is formed on a pressure side lip of the tip pocket.
  • a third heat transfer augmentation device is formed on a floor of the tip pocket.
  • a plurality of cooling holes fluidly connect the tip pocket to at least one internal cooling cavity formed inside the airfoil.
  • the plurality of cooling holes are positioned relative to a central axis of the tip pocket, and a wall of the heat transfer augmentation device terminates prior to intersecting the central axis.
  • At least one of the plurality of cooling holes is angled relative to a floor of the tip pocket.
  • the heat transfer augmentation device is slanted at an angle relative to a floor of the tip pocket.
  • the heat transfer augmentation device includes a ramp that divides a floor of the tip pocket into radially offset floor portions.
  • a gas turbine engine includes, among other things, an airfoil including a tip pocket formed at a tip of the airfoil.
  • the tip pocket extends from a position near a leading edge of the airfoil to a position that is upstream from a trailing edge of the airfoil.
  • a plurality of heat transfer augmentation devices are formed in the tip pocket.
  • the tip pocket extends from a position near the leading edge to a position near a mid-span of the airfoil.
  • the plurality of heat transfer augmentation devices are formed on a floor of the tip pocket.
  • the plurality of heat transfer augmentation devices are formed on a suction side wall of the tip pocket.
  • the plurality of heat transfer augmentation devices are formed on a pressure side wall of the tip pocket.
  • the plurality of heat transfer augmentation devices are formed on at least two of a floor, a suction side wall and a pressure side wall of the tip pocket.
  • a cooling hole fluidly connects the tip pocket to at least one internal cooling cavity formed inside the airfoil.
  • the plurality of heat transfer augmentation devices terminate prior to intersecting a central axis of the tip pocket.
  • the cooling hole is angled relative to a floor of the tip pocket.
  • the plurality of heat transfer augmentation devices are slanted at an angle relative to a floor of the tip pocket.
  • the plurality of heat transfer augmentation devices includes ramps that divide a floor of the tip pocket into radially offset floor portions.
  • a method of cooling a gas turbine engine component includes, among other things, communicating a cooling fluid into a tip pocket formed at a tip of an airfoil, temporarily blocking the cooling fluid within the tip pocket with at least one heat transfer augmentation device, and expelling the cooling fluid from the tip pocket into a gas stream.
  • a tip pocket is formed at a tip of the airfoil.
  • the tip pocket may include one or more heat transfer augmentation devices, such as trip strips, chevrons, or the like, disposed within the tip pocket.
  • the heat transfer augmentation devices may be formed on a suction or pressure side lip of the tip pocket, a floor of the tip pocket, or any combination of locations.
  • FIG. 1 schematically illustrates a gas turbine engine 20.
  • the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
  • Alternative engines might include an augmenter section (not shown) among other systems or features.
  • the fan section 22 drives air along a bypass flow path B in a bypass duct defined within a nacelle 15, while the compressor section 24 drives air along a core flow path C for compression and communication into the combustor section 26 then expansion through the turbine section 28.
  • the exemplary engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided, and the location of the bearing systems 38 may be varied as appropriate to the application.
  • the low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42, a first (or low) pressure compressor 44 and a first (or low) pressure turbine 46.
  • the inner shaft 40 is connected to the fan 42 through a speed change mechanism, which in exemplary gas turbine engine 20 is illustrated as a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30.
  • the high speed spool 32 includes an outer shaft 50 that interconnects a second (or high) pressure compressor 52 and a second (or high) pressure turbine 54.
  • a combustor 56 is arranged in exemplary gas turbine 20 between the high pressure compressor 52 and the high pressure turbine 54.
  • a mid-turbine frame 57 of the engine static structure 36 is arranged generally between the high pressure turbine 54 and the low pressure turbine 46.
  • the mid-turbine frame 57 further supports bearing systems 38 in the turbine section 28.
  • the inner shaft 40 and the outer shaft 50 are concentric and rotate via the bearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes.
  • the core airflow is compressed by the low pressure compressor 44 then the high pressure compressor 52, mixed and burned with fuel in the combustor 56, then expanded over the high pressure turbine 54 and low pressure turbine 46.
  • the mid-turbine frame 57 includes airfoils 59 which are in the core airflow path C.
  • the turbines 46, 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion.
  • gear system 48 may be located aft of combustor section 26 or even aft of turbine section 28, and fan section 22 may be positioned forward or aft of the location of gear system 48.
  • the engine 20 in one example is a high-bypass geared aircraft engine.
  • the engine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than about ten (10)
  • the geared architecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3
  • the low pressure turbine 46 has a pressure ratio that is greater than about five.
  • the engine 20 bypass ratio is greater than about ten (10:1)
  • the fan diameter is significantly larger than that of the low pressure compressor 44
  • the low pressure turbine 46 has a pressure ratio that is greater than about five 5:1.
  • Low pressure turbine 46 pressure ratio is pressure measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle.
  • the gear system 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans and turboshafts.
  • the fan section 22 of the engine 20 is designed for a particular flight condition -- typically cruise at about 0.8 Mach and about 35,000 feet (10,668 meters).
  • the flight condition of 0.8 Mach and 35,000 ft, with the engine at its best fuel consumption - also known as "bucket cruise Thrust Specific Fuel Consumption ('TSFC')" - is the industry standard parameter of lbm of fuel being burned divided by lbf of thrust the engine produces at that minimum point.
  • “Low fan pressure ratio” is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system.
  • the low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45.
  • Low corrected fan tip speed is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram °R) / (518.7 °R)] 0.5 .
  • the "Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1,150 ft/second (350.5 meters/second).
  • Each of the compressor section 24 and the turbine section 28 may include alternating rows of rotor assemblies and vane assemblies (shown schematically).
  • the rotor assemblies can carry a plurality of rotating blades 25, while each vane assembly can carry a plurality of vanes 27 that extend into the core flow path C.
  • the blades 25 may either create or extract energy in the form of pressure from the core airflow as it is communicated along the core flow path C.
  • the vanes 27 direct the core airflow to the blades 25 to either add or extract energy.
  • Figure 2 illustrates a component 58 that can be employed for use within a gas turbine engine, such as the gas turbine engine 20 of Figure 1 .
  • the component 58 is a turbine blade.
  • the various features of this disclosure are applicable to other components located elsewhere within a gas turbine engine, such as vanes or compressor airfoils. Thus, some features that are particularly relevant to the illustrated turbine blade are to be considered optional and are not necessary to practice this disclosure.
  • the component 58 includes a platform 60, an airfoil 62 that extends in a first direction from the platform 60, and a root 64 that extends in a second, opposite direction from the platform 60.
  • the airfoil 62 includes a leading edge 66, a trailing edge 68, a pressure sidewall 70 and a suction sidewall 72.
  • the pressure sidewall 70 and the suction sidewall 72 are spaced apart and generally meet together at both the leading edge 66 and the trailing edge 68.
  • the airfoil 62 connects to the platform 60 at a fillet 69.
  • the root 64 connects to the platform 60 at buttresses 71.
  • the root 64 may include a neck 73 and one or more serrations 75 for securing the component 58 to a disk (not shown).
  • the component 58 may include multiple internal cooling cavities 74A, 74B and 74C.
  • the internal cooling cavities 74A, 74B and 74C are core formed cavities that extend inside of the airfoil 62.
  • the internal cooling cavities 74A, 74B and 74C may form part of an internal cooling circuit 81 for cooling the component 58.
  • the exemplary internal cooling circuit 81 of the component 58 represents but one non-limiting example of the many potential cooling circuits that may be formed inside the component 58.
  • the component 58 could be cast to include various alternative cooling cavities and internal circuitry configurations within the scope of this disclosure
  • the airfoil 62 extends to a tip 77.
  • the tip 77 can be referred to as the outer diameter portion of the component 58.
  • the root 64 can be referred to as the inner diameter portion of the component 58.
  • a tip pocket 80 may be formed in the tip 77 of the airfoil 62.
  • the tip pocket 80 may also be referred to as a squealer pocket.
  • the tip pocket 80 is part of the internal cooling circuit 81 of the component 58.
  • the tip pocket 80 introduces a cooling fluid at the tip 77 of the airfoil 62 to cool the tip 77 and avoid airfoil tip burning.
  • FIGS 3, 4 and 5 illustrate an exemplary tip 77 of an airfoil 62.
  • a tip pocket 80 is formed within the tip 77.
  • a cooling fluid F may be directed into the tip pocket 80 to cool the tip 77.
  • the tip pocket 80 terminates prior to, or upstream from, the trailing edge 68 of the airfoil 62. In one embodiment, the tip pocket 80 extends from a position near the leading edge 66 of the airfoil 62 to a position near a mid-span M of the airfoil 62 (see Figure 3 ). However, the axial, circumferential and radial dimensions of the tip pocket 80 may vary within the scope of this disclosure.
  • the tip pocket 80 may include a suction side lip 82, a pressure side lip 84, a leading edge lip 86 and a trailing edge lip 88.
  • the suction side lip 82, the pressure side lip 84, the leading edge lip 86 and the trailing edge lip 88 extend radially outwardly from a floor 90 of the tip pocket 80.
  • the tip pocket 80 may include one or more heat transfer augmentation devices 92.
  • the heat transfer augmentation device 92 is a trip strip.
  • other augmentation devices are also contemplated as being within the scope of this disclosure (see, for example, Figure 18 and 19 ).
  • the heat transfer augmentation device 92 axially extends across the suction side lip 82 of the tip pocket 80 between the leading edge lip 86 and the trailing edge lip 88.
  • the pressure side lip 84 could alternatively or additionally include a heat transfer augmentation device 92.
  • cooling holes 94 may extend through the floor 90 of the tip pocket 80 to fluidly connect the tip pocket 80 with one or more internal cooling cavities 74 that are formed inside the airfoil 62.
  • the cooling holes 94 may communicate a cooling fluid F from the internal cooling cavities 74 into the tip pocket 80.
  • a portion of the cooling holes 94 may be angled relative to the floor 90 and the internal cooling cavities 74.
  • the heat transfer augmentation device(s) 92 are adapted to temporarily trap the cooling fluid F inside the tip pocket 80.
  • the heat transfer augmentation device(s) 92 may temporarily block the cooling fluid F prior to its ejection into a gas stream GS (see Figure 4 ).
  • some of the cooling fluid F may ricochet back toward the floor 90 after contacting the heat transfer augmentation device(s) 92, thereby increasing the amount of time the cooling fluid F stays within the tip pocket 80.
  • the heat transfer augmentation device(s) 92 also augment the heat transfer of the cooling fluid F in the tip pocket 80.
  • FIGS 6, 7 and 8 illustrate another tip 177 of an airfoil 162.
  • like reference numbers designate like elements where appropriate and reference numerals with the addition of 100 or multiples thereof designate modified elements that are understood to incorporate the same features and benefits of the corresponding original elements.
  • a tip pocket 180 is formed at the tip 177 and includes multiple heat transfer augmentation devices 192.
  • the heat transfer augmentation devices 192 are formed on both a suction side lip 182 and a pressure side lip 184 of the tip pocket 180 and may extend radially outwardly from a floor 190 of the tip pocket 180. In other words, the heat transfer augmentation devices 192 of this embodiment extend vertically. The heat transfer augmentation devices 192 may extend to the same height as the suction side lip 182 and the pressure side lip 184, in one embodiment.
  • a plurality of cooling holes 194 extend through the floor 190 of the tip pocket 180.
  • the cooling holes 194 may be positioned along a central axis CA of the tip pocket 180 (see Figure 6 ) or could be offset from the central axis (see Figures 21 and 24 ).
  • Each heat transfer augmentation device 192 may include a wall 195 that faces toward the cooling holes 194. In one embodiment, the walls 195 terminate prior to intersecting the central axis CA. Put another way, the thickness of each heat transfer augmentation device 192 does not extend beyond the cooling holes 194.
  • FIGS 9, 10, 11 , 12, 13 and 14 illustrate another tip 277 of an airfoil 262.
  • a tip pocket 280 is formed at the tip 277 and includes multiple heat transfer augmentation devices 292.
  • the heat transfer augmentation devices 292 are formed on both a suction side lip 282 and a pressure side lip 284 of the tip pocket 280 and may extend radially outwardly from a floor 290 of the tip pocket 280.
  • the heat transfer augmentation devices 292 may be slanted toward either a leading edge lip 286 of the tip pocket 280 (see Figures 9-11 ) or a trailing edge lip 288 of the tip pocket 280 (see Figures 12-14 ).
  • the heat transfer augmentation devices 292 are slanted at about a 45° angle relative to the floor 290. Of course, other slant angles are also contemplated.
  • FIGS 15, 16 and 17 illustrate yet another tip 377 of an airfoil 362.
  • a tip pocket 380 is formed at the tip 377 and includes a plurality of heat transfer augmentation devices 392.
  • the heat transfer augmentation devices 392 are formed on a floor 390 of the tip pocket 380. The heat transfer augmentation devices 392 help mitigate aftward flow of the cooling fluid F and increase surface area of the tip pocket 380.
  • the heat transfer augmentation devices 392 may extend from a suction side lip 382 to a pressure side lip 384 of the tip pocket 380. That is, the heat transfer augmentation devices 392 may span an entire distance between the suction side lip 382 and the pressure side lip 384.
  • the heat transfer augmentation devices 392 are tapered.
  • the heat transfer augmentation devices 392 may taper toward a central axis CA of the tip pocket 380. This taper may simplify the casting of the heat transfer augmentation devices 392 within the tip pocket 380.
  • FIGS 18 and 19 illustrate yet another tip 477 of an airfoil 462.
  • a tip pocket 480 is formed at the tip 477 and includes a plurality of heat transfer augmentation devices 492.
  • the heat transfer augmentation devices 492 are formed on a floor 490 of the tip pocket 480.
  • the heat transfer augmentation devices 492 of this embodiment are chevrons.
  • the heat transfer augmentation devices 492 may point toward a leading edge lip 486 (see Figure 19 ) or a trailing edge lip 488 (see Figure 18 ) of the tip pocket 480.
  • the tip pocket 580 is disposed at a tip 577 of an airfoil 562.
  • the tip pocket 580 includes a plurality of heat transfer augmentation devices 592 that are disposed at each of a floor 590, a suction side lip 582 and a pressure side lip 584 of the tip pocket 580.
  • FIGS 21, 22 and 23 illustrate another tip 677 of an airfoil 662.
  • a tip pocket 680 is formed at the tip 677 and may include one or more heat transfer augmentation devices 692.
  • the heat transfer augmentation device 692 helps mitigate aftward flow of the cooling fluid F and increases surface area of the tip pocket 680.
  • the heat transfer augmentation device 692 may extend at any angle between a suction side lip 682 and a pressure side lip 684 of the tip pocket 680.
  • the heat transfer augmentation device 692 is formed by a stepped portion of a floor 690 of the tip pocket 680.
  • the heat transfer augmentation device 692 may include a ramp 691 that extends between a first portion 693 and a second portion 695 of the floor 690.
  • the first portion 693 and the second portion 695 of the floor 690 are radially offset from one another. In other words, the first portion 693 and the second portion 695 of the floor 690 extend in different planes.
  • the tip pocket 780 is disposed at a tip 777 of an airfoil 762.
  • the tip pocket 780 includes heat transfer augmentation devices 792 that extend from a suction side lip 782 and a pressure side lip 784 of the tip pocket 780.
  • Cooling holes 794 may extend through a floor 790 of the tip pocket 780 to fluidly connect the tip pocket 780 with an internal cooling cavity 774.
  • the cooling holes 794 may communicate a cooling fluid F from the internal cooling cavity 774 into the tip pocket 780.
  • Cooling hole portions P1 and P2 of the cooling holes 794 may be angled relative to the floor 790 and the internal cooling cavity 774.
  • the angled cooling holes 794 are angled at a relatively shallow angle ⁇ . Cooling holes of such a shallow angle cannot typically be cast or drilled into the tip pocket 780. However, these angled cooling holes 794 can be manufactured by using an additive manufacturing process.
  • the tip wall configurations of Figures 3-24 are intended as non-limiting embodiments only. Any configuration shown by these Figures may be used in combination with a configuration of any other Figure to create a desired tip cooling effect.
  • the heat transfer augmentation devices increase the amount of time the cooling fluid is maintained within the tip pocket and augment the heat transfer of the cooling fluid.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP15001485.0A 2014-05-16 2015-05-18 Bauteil eines gasturbinentriebwerks, zugehöriges gasturbinentriebwerk und kühlverfahren Active EP2944764B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US201461994270P 2014-05-16 2014-05-16

Publications (3)

Publication Number Publication Date
EP2944764A1 true EP2944764A1 (de) 2015-11-18
EP2944764A8 EP2944764A8 (de) 2017-06-07
EP2944764B1 EP2944764B1 (de) 2021-04-28

Family

ID=53180497

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15001485.0A Active EP2944764B1 (de) 2014-05-16 2015-05-18 Bauteil eines gasturbinentriebwerks, zugehöriges gasturbinentriebwerk und kühlverfahren

Country Status (2)

Country Link
US (4) US10012089B2 (de)
EP (1) EP2944764B1 (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3118414A1 (de) * 2015-07-02 2017-01-18 United Technologies Corporation Gasturbinentriebwerksschaufel
EP3121377A1 (de) * 2015-07-23 2017-01-25 United Technologies Corporation Turbinenrotoren mit einer turbinenschaufeln mit gekühlten turbulatorspitzentaschen
WO2017146680A1 (en) * 2016-02-23 2017-08-31 Siemens Aktiengesellschaft Turbine blade squealer tip with vortex disrupting fence
CN110566284A (zh) * 2019-10-09 2019-12-13 西北工业大学 一种带阻隔肋的凹槽叶顶结构
CN112922674A (zh) * 2021-02-04 2021-06-08 南京航空航天大学 一种具有气膜冷却凹槽的涡轮叶片
EP4006304A1 (de) * 2020-11-26 2022-06-01 Pratt & Whitney Canada Corp. Turbinenlaufschaufel for ein gasturbinentriebwerk und gasturbinentriebwerk

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150345301A1 (en) * 2014-05-29 2015-12-03 General Electric Company Rotor blade cooling flow
DE112016004421B4 (de) * 2015-09-29 2021-10-21 Mitsubishi Power, Ltd. Laufschaufel und damit ausgestattete gasturbine
US10801331B2 (en) * 2016-06-07 2020-10-13 Raytheon Technologies Corporation Gas turbine engine rotor including squealer tip pocket
US10400608B2 (en) * 2016-11-23 2019-09-03 General Electric Company Cooling structure for a turbine component
US11021967B2 (en) * 2017-04-03 2021-06-01 General Electric Company Turbine engine component with a core tie hole
US20190003316A1 (en) * 2017-06-29 2019-01-03 United Technologies Corporation Helical skin cooling passages for turbine airfoils
KR101985093B1 (ko) * 2017-09-12 2019-05-31 두산중공업 주식회사 블레이드 팁의 실링구조와 이를 포함하는 가스터빈
KR20190127024A (ko) * 2018-05-03 2019-11-13 두산중공업 주식회사 터빈 블레이드 및 상기 터빈 블레이드를 포함하는 가스 터빈
US20190368359A1 (en) * 2018-06-05 2019-12-05 United Technologies Corporation Squealer shelf airfoil tip
US10961854B2 (en) * 2018-09-12 2021-03-30 Raytheon Technologies Corporation Dirt funnel squealer purges
US11118462B2 (en) * 2019-01-24 2021-09-14 Pratt & Whitney Canada Corp. Blade tip pocket rib
US11659043B1 (en) 2022-01-27 2023-05-23 Meta Platforms Technologies, Llc Systems and methods for predictively downloading volumetric data
EP4311914A1 (de) * 2022-07-26 2024-01-31 Siemens Energy Global GmbH & Co. KG Turbinenlaufschaufel

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19963375A1 (de) * 1999-12-28 2001-07-12 Abb Alstom Power Ch Ag Schaufel für den Rotor einer Gasturbine sowie Gasturbine mit einer solchen Schaufel
US20030021684A1 (en) * 2001-07-24 2003-01-30 Downs James P. Turbine blade tip cooling construction
US20080044289A1 (en) * 2006-08-21 2008-02-21 General Electric Company Tip ramp turbine blade
WO2010010284A1 (fr) * 2008-07-21 2010-01-28 Turbomeca Aube creuse de roue de turbine comportant une nervure, roue et turbomachine associees
US20100111704A1 (en) * 2008-10-30 2010-05-06 Mitsubishi Heavy Industries, Ltd. Turbine blade having squealer
US20120076653A1 (en) * 2010-09-28 2012-03-29 Beeck Alexander R Turbine blade tip with vortex generators
US8435004B1 (en) * 2010-04-13 2013-05-07 Florida Turbine Technologies, Inc. Turbine blade with tip rail cooling
EP2666968A1 (de) * 2012-05-24 2013-11-27 General Electric Company Turbinenlaufschaufel
EP2666967A1 (de) * 2012-05-24 2013-11-27 General Electric Company Turbinenlaufschaufel
US20140030102A1 (en) * 2012-07-26 2014-01-30 General Electric Company Turbine bucket with notched squealer tip
US20140030101A1 (en) * 2012-07-26 2014-01-30 General Electric Company Turbine bucket with squealer tip
WO2015069411A1 (en) * 2013-11-11 2015-05-14 United Technologies Corporation Gas turbine engine turbine blade tip cooling

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7739162B1 (en) * 2001-05-04 2010-06-15 West Corporation System, method, and business method for setting micropayment transaction to a pre-paid instrument
US7537431B1 (en) 2006-08-21 2009-05-26 Florida Turbine Technologies, Inc. Turbine blade tip with mini-serpentine cooling circuit
US8011889B1 (en) 2007-09-07 2011-09-06 Florida Turbine Technologies, Inc. Turbine blade with trailing edge tip corner cooling
US9228442B2 (en) 2012-04-05 2016-01-05 United Technologies Corporation Turbine airfoil tip shelf and squealer pocket cooling
US10408066B2 (en) 2012-08-15 2019-09-10 United Technologies Corporation Suction side turbine blade tip cooling
JP6168746B2 (ja) * 2012-10-10 2017-07-26 キヤノン株式会社 スイッチング電源及びスイッチング電源を備えた画像形成装置

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19963375A1 (de) * 1999-12-28 2001-07-12 Abb Alstom Power Ch Ag Schaufel für den Rotor einer Gasturbine sowie Gasturbine mit einer solchen Schaufel
US20030021684A1 (en) * 2001-07-24 2003-01-30 Downs James P. Turbine blade tip cooling construction
US20080044289A1 (en) * 2006-08-21 2008-02-21 General Electric Company Tip ramp turbine blade
WO2010010284A1 (fr) * 2008-07-21 2010-01-28 Turbomeca Aube creuse de roue de turbine comportant une nervure, roue et turbomachine associees
US20100111704A1 (en) * 2008-10-30 2010-05-06 Mitsubishi Heavy Industries, Ltd. Turbine blade having squealer
US8435004B1 (en) * 2010-04-13 2013-05-07 Florida Turbine Technologies, Inc. Turbine blade with tip rail cooling
US20120076653A1 (en) * 2010-09-28 2012-03-29 Beeck Alexander R Turbine blade tip with vortex generators
EP2666968A1 (de) * 2012-05-24 2013-11-27 General Electric Company Turbinenlaufschaufel
EP2666967A1 (de) * 2012-05-24 2013-11-27 General Electric Company Turbinenlaufschaufel
US20140030102A1 (en) * 2012-07-26 2014-01-30 General Electric Company Turbine bucket with notched squealer tip
US20140030101A1 (en) * 2012-07-26 2014-01-30 General Electric Company Turbine bucket with squealer tip
WO2015069411A1 (en) * 2013-11-11 2015-05-14 United Technologies Corporation Gas turbine engine turbine blade tip cooling

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3118414A1 (de) * 2015-07-02 2017-01-18 United Technologies Corporation Gasturbinentriebwerksschaufel
US10053992B2 (en) 2015-07-02 2018-08-21 United Technologies Corporation Gas turbine engine airfoil squealer pocket cooling hole configuration
EP3121377A1 (de) * 2015-07-23 2017-01-25 United Technologies Corporation Turbinenrotoren mit einer turbinenschaufeln mit gekühlten turbulatorspitzentaschen
WO2017146680A1 (en) * 2016-02-23 2017-08-31 Siemens Aktiengesellschaft Turbine blade squealer tip with vortex disrupting fence
CN110566284A (zh) * 2019-10-09 2019-12-13 西北工业大学 一种带阻隔肋的凹槽叶顶结构
EP4006304A1 (de) * 2020-11-26 2022-06-01 Pratt & Whitney Canada Corp. Turbinenlaufschaufel for ein gasturbinentriebwerk und gasturbinentriebwerk
CN112922674A (zh) * 2021-02-04 2021-06-08 南京航空航天大学 一种具有气膜冷却凹槽的涡轮叶片

Also Published As

Publication number Publication date
US20200291793A1 (en) 2020-09-17
EP2944764B1 (de) 2021-04-28
US11156101B2 (en) 2021-10-26
EP2944764A8 (de) 2017-06-07
US20150330228A1 (en) 2015-11-19
US20180274373A1 (en) 2018-09-27
US10633981B2 (en) 2020-04-28
US11661853B2 (en) 2023-05-30
US20220003120A1 (en) 2022-01-06
US10012089B2 (en) 2018-07-03

Similar Documents

Publication Publication Date Title
US11661853B2 (en) Airfoil tip pocket with augmentation features
US10041358B2 (en) Gas turbine engine blade squealer pockets
EP3043027B1 (de) Gasturbinenmotorkomponente mit konformem kehlkühlungspfad
EP2944761B1 (de) Gasturbinenmotorkomponente mit plattformkühlung
EP3042041B1 (de) Gasturbinenmotorflügelturbulator für flügelkriechbeständigkeit
EP3009616A1 (de) Gasturbinenbauteil mit plattformkühlung
EP2993304A1 (de) Gasturbinenmotorkomponente mit filmkühlungsloch
EP3112596A1 (de) Gasturbinenmotorschaufel mit biaxialem wandkühlkanal und zugehöriger gasturbinenmotor
EP3009600A1 (de) Turbinenschaufel mit spitzenkühlung eines gasturbinentriebwerks
EP3054093B1 (de) Anordnung von turbulatoren
US20160003055A1 (en) Gas turbine engine component cooling with interleaved facing trip strips
EP3051066A1 (de) Gusskern mit versetzten fortsätzen
EP2993303A1 (de) Gasturbinenmotorkomponente mit filmkühlloch mit tasche
US11149548B2 (en) Method of reducing manufacturing variation related to blocked cooling holes
EP2927429A1 (de) Gasturbinenkomponente mit flusstrennungsrippe
WO2015050729A1 (en) Turbine vane with platform rib
WO2015047576A1 (en) Diffused platform cooling holes
EP3581762B1 (de) Kühlkanalanordnung für gasturbinendeckband
EP2977557A1 (de) Gekühlte schaufelstruktur und zugehöriges kühlverfahren
EP2975222A1 (de) Gekühlte tasche in einer turbinenschaufelplattform
EP2942486A1 (de) Konfiguration des kühlkanals einer gasturbinenmotorschaufel

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIN1 Information on inventor provided before grant (corrected)

Inventor name: GAUTSCHI, STEVEN BRUCE

Inventor name: PROPHETER-HINCKLEY, TRACY A.

Inventor name: QUACH, SAN

17P Request for examination filed

Effective date: 20160517

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

RIN1 Information on inventor provided before grant (corrected)

Inventor name: PROPHETER-HINCKLEY, TRACY A.

Inventor name: QUACH, SAN

Inventor name: GAUTSCHI, STEVEN BRUCE

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: UNITED TECHNOLOGIES CORPORATION

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/20 20060101AFI20200212BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20200604

RIN1 Information on inventor provided before grant (corrected)

Inventor name: GAUTSCHI, STEVEN BRUCE

Inventor name: PROPHETER-HINCKLEY, TRACY A.

Inventor name: QUACH, SAN

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTC Intention to grant announced (deleted)
INTG Intention to grant announced

Effective date: 20201113

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: RAYTHEON TECHNOLOGIES CORPORATION

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602015068549

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1387254

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210515

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1387254

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210428

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210728

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210828

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210729

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210830

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210728

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20210428

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210531

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210518

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210531

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602015068549

Country of ref document: DE

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20210531

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20220131

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210518

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210828

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20150518

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230520

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20240419

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240418

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20240418

Year of fee payment: 10

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210428